Pneumatic aircraft-propelling means



2 Sh eets -Sheet 1 0. K. QUAST PNEUMATIC AIRCRAFT PROPELLING MEANS Filed Oct.

Dec. 16, 1930,

Inventor H0 /(ar/ Qua szv Dec. 16, 1930.

O. K QUAST PNEUMATIC AIRCRAFT PROPELLING MEANS Filed Oct 2 Sheets-Sheet 2 Inventor Attorney 0H0 Karl Quasi By W UNITED-1: m

Patented lien. 16, 1930 j;

o'r'ro KAnLf'eunsT, or 'sroxhuniwii'srrmerofi i rivi iuivmrrcfAIncRArr rnorEnLrNe MEANS" My invention relateswtopneumatic air-,c craftpropelling means and the principal objects ofthe invention are to provide, in (301115 bination with air-craft, a plurality of novel propellers :comprising vacuum means for drawing airtherein from above with considerable force whereb-v va (vertical or upward lift isexerted on said air-craft, and means for discharging said; airthrough the wings of the air-craft at great velocity against the surrounding air wherebythe saidair-craftis pro:

jected through space, Further objects of the invention are to 'provide,in combination withthe, propelling Ineans an air-craft of a novel body and wing construction together with other novel details and arrangements as hereinafter set forth.

WVith the above and otheri objects -in---view which will appearas the; description;proa .ceeds, theinventionconsists of the novel .con fl; struction, adaptation, combination. and ar-c rangement of parts hereinafter-described and;

. claimed. Theseobjects areaccomplished by.

. Fig. 3 is a viewiin fronte'nd envanon;

Fig. 4. is a view in transverse vvertlcal. s'ec-, tiontaken substantlally onja broken :hne:

i I housing removed; 7

n Fig. 6 is a similar vlew with; the outer sleeve of the invention; Fig. 2 1s a View 1n same;

one of the propellers andt aken' on'a broken line 5, 5 of Fig. 7 with theouter sleeve and and housing intact 7 Fig.7 is a view 1n vertical section of one of the propeller devices taken'on a broken line.

7,7ofFig6; v Fig. 8 is a fragmentaryplan View showing air intake ports; and r side elevation iof the .Figri9 is a view in vertical section taken on abrokenline 9, 9 offFj g Y .Referring to: the drawings;;throughout {which like reference numerals designate like parts, the numeral 5 indicates the nain body ofthe'air-craft which is roundin. cross section and which tapers from asemi-globular head to a pointed tailwhich'is providedwith the usual steering vanes Atthe-forward'end of said bodyjl prefer to provide anupperggill wing 6 and a corresponding loweriwing 7." Said wings are j'relatively small andrrnayhave a slight] upward inclination whereby vthey will assist: in lifting the forward or. heavier end ofthdairgcral'tbody in" itsapassage throughthe' air as will be 11I1der'stood-.-

The numeral 8 designates the main body :wing of the air-craft which extends correspondingly on .both sides of; the; main body 5 anda greaterportion thereof.;' Said gwirig converges toward the rear end .ofthe. aircraft audits-outer or side edge portions are :1PI'OVld6dj with a plurality 'of corresponding devices illustrated; in. the accompanying :d W g ;W r i :T-' 1 "Figure 1 is a top plan viewof anlair-craftf' showing in outline the general arrangement,

steps 9 forreasonspresently setforth r It may! here be stated that theprirnary feature of niyinventionresides in its mode of propulsion-which consists essentially in fdrawing-air into the device and discharging same. atavery high velocity; In the embodi- Ument ofthissfeature aplu'rality of air pro pellermechanisms,designated as, a whole by the numeral 10 aredisposed within the aircraft body nOrdinarijly one. of such pro- 1 i I .pe11ers; is provided foriieachoppositely dis Fig. 5-is a view in vertical section showing posed pair of wing steps 9 and one ioreachfQf the gill wings 6 and? ;An= air intake 11 extends downwardly through ,the body 5 to at"13,-.whereby the air expands as it. is dischargedtherefroni, I Said air intakes may extend from aforward directionjto the propellersTlocatIQdj in the forward end of the aircraft'bodygand the exhaust conduits extend to the rear edge portions of the gill wings 6 and 7. Thus the air sucked into the propellers from above will have'a lifting effect on theair-craft while its discharge therefrom in a rear direction against the surrounding outside air at great velocity will drive the air-craft ahead.

The propeller devices 10 which furnish the motive power for the aircraft comprise a shaft 14 to one end of which is fixed a pulley 15 whereby power may be appliedfrom. any desired and suitable source. Said shaft is mounted in bearings 16 on ithe sides of astationary cylindrical housing comprising an inner drum 17 disposed 1n 660611 7 1116 relatlonu with said shaft and anouter. drum 181nte-' gral with said inner dr-um -and concentric relation with the shaft. i i

A cylindrical rotorxmegmher 19 has four integral radial wings;20, dividing said rotor intoyfour equalparts, that "are 'secured to pins 24 fixed thereto and slidably disposedwithin-holes in the wings 2Q. A- spring 25 is aflcentralhub 21 which is keyed to the shaft '14; Each of said wings'is correspondingly recessed orslotted from itsouter end to receive vanes 22 that are slidably disposed within said-slots. Theexterior edge portion of said vanes has an antifriction roller 23 mounted therein and said rollers; are J adapted to engage-the interior "cylindrical wall of the inner drum"17-.- Each of said vanes is provided on its inner edge -with a pair of loc'ated in the-bottom'of each'ofsaid holes and-normally in-compression against: the ends of said pins whereby the vanes will be imp'elled outwardly thus keeping the anti-frict'ion rollers in continuous engagement Jwith ysaid inner drum as will lee-understood Entry ports-26 are provided in the top of" the cylindrical'housing through the drums 17 =and=18 that register with the intake 11. An

exhaust pipe 27 extends from the inner drum 17 "to acommunicationwith the exhaust -conduit'=12. T-huswhen the rotor member 19 *isrotating in aclockwise direction, as indi cated'by-the arrow in Fig. "6,'the vanes 22 will'trap theair entering throughthe top 1ntake and carry it around in the'eccentrlc chamber betweensaid rotor and the inner drum 17' and force it out through the exhaust whereby it -is discharged through the expanded outlets 13"a'tconsiderable velocity.

A rotary "casing =or :sleeve '28 ffits snugly around-the outerdrum 18 of the stationary; housing and its end is keyed or otherwise fixed to the shaft 14'at 29. iSaid casing re- *volves with said 'shaft and around said stationaryThousing and isiprovide'd with a plurality of'spaced slots 30 that correspond wlth the entry ports '26,

" number and are positioned to register with saidlen-try port slightly in advance of each of the-vanes '22 and te close said port an in'stant aheado f the time-that'said vanesireach the en- 'Said slots are four in ler mechanisms aresof timed as to alternately reach the intake and exhaust strokeswhereby their impulses will be smooth and continuous in .the operation of the device as a whole.

" Having 'thus' described my invention, it being vunderstood-that minor changesmay be resorted to in its construction without dewparting from" its ,scope and spirit, what I claim and desire to secure by Letters Patent of the United States is V '1. The combination of an air-craft having a round body, tapering from a semi-globular head toa pointed tail, relatively small upper and lower' gill' wings adjacent said head, a relatively large wingextendinga greater portion of the body, stepsforming the outer edges of saidw ing, aplurality of rotarypropelling mechanisms mounted withinthe body,

vacuum means for forcibly drawing air from above into said mechanisms, discharge means for forcibly expelling the air rearwardly "through the steps 0f the large wing, and intake and "discharge means for the propelling mechanisms of the gill wings.

Q2. The comb nation with' an air-craft of pneumatic air-craft propelling means con- ;sistingofiaplurality of power driven propelling mechanisms each comprisingastationary cylindrical housing =having an inner and an L outer drum,-a shaft concentric with the outer drum and eccentric-with the inner drum, a

cylindrical rotor member for said shaft withinthe inner drum,-radial-wings for the rotor,

a spring impelled vane for each rotor wing arranged toyengage the inner wall of the inner drum', an'e'ntryaport above the propelling mechanism and in communication with the inner drum, an exhaust conduit extending from the inner drum to outlets in the wings of-th e-air-craft, a sleeve for the cylindrical housing fixed to the shaft and'having spaced slotsadapted to register with the air entry .port, and said slots arranged to open and close said entry port slightly "in advance of each of=said-vanes;- V

3. The combinationwith an air-craft of pneumatic air-craft'propelling meansconsisting'o'f :a plurality of power driven propellingmechanisms each comprising a stationary 1 cylindrical housing having an inner and an outer drum, ashaft concentric with the outer drum and eccentric with the inner drum, a

cylindrical rotor memberflforsaid shaft within the inner drum, radial wings {for the rotor,

a spring impelled vane for each rotor wing arranged to engage the inner Wall of the in-- ner drum, anti-friction rollers for said vanes, I

an entry port above the propellingmechanism and in communication with the inner drum, an exhaust conduit extending ,from the inner drum to outlets in the wings of the air-craft, asleeve for the cylindrical 7 housing fixed to the shaft and having a a plurality of spaced slots adapted to register with the air entry port, and said slots arranged to open and close the entry port slightly in advance of eachof said vanes. v In testimony whereof I afiix my'signature.

-- OTTO KARL 'QUAST. 

